Currently, there is a trend towards the creation of production facilities and the conduct of various research based on orbital complexes, spacecraft, separate scientific modules, and laboratories. One of the ways to deliver the results of such research can be a small reentry vehicle (SRV). For the proper formation of the SRV's design, it is necessary at the initial stages of design to select the landing system components based on the tasks to be solved by the SRV and the requirements imposed by the payload. For this purpose, this study investigates the possibility of determining the aerodynamic characteristics of bodies, in particular, the elements of the landing system of the reentry vehicle, using vortex methods. To assess the feasibility and adequacy of the methods considered, they are used to solve two-dimensional and three-dimensional flow problems around wing profiles. The study presents methods for assessing the aerodynamic characteristics of two- dimensional and three-dimensional bodies using vortex methods. Algorithms for constructing a calculation scheme based on the geometry of the body are provided. Software has been developed based on these algorithms for two-dimensional and three-dimensional methods, implementing the algorithms presented in the article. The developed software has been verified according to experimental results and results obtained using other software.